Results
2024-05-13: The FAA is adopting a new airworthiness directive (AD) for all Embraer S.A. Model EMB-545 and EMB-550 airplanes. This AD was prompted by a report of a hard landing event with substantial damage to the airplane, in which the angle of attack (AOA) limiter was engaged during the final approach phase in unstable air conditions and remained engaged until the airplane touched down on the runway. This AD requires revising the Limitations and Normal Procedures sections of the existing airplane flight manual (AFM) to incorporate new operational airspeed limitations, and flight control limitations and approach procedures when AOA limiter protection is engaged, as specified in an Ag[ecirc]ncia Nacional de Avia[ccedil][atilde]o Civil (ANAC) AD, which is incorporated by reference. This AD also requires inspecting records for instances of AOA limiter engagement during a certain phase of flight and reporting findings to the FAA. The FAA is issuing this AD to address the unsafe condition on these products.
76-22-09: 76-22-09 GRUMMAN AMERICAN: Amendment 39-2761. Applies to Model AA-5A serial numbers AA5A-001 through AA5A-0227 and Model AA-5B serial numbers AA5B-0111 through AA5B-0359 airplanes certificated in all categories. Compliance required before further flight. To prevent continued use of certain Stewart Warner oil coolers which may be defective, accomplish the following: (a) Remove the cowl assembly as necessary to gain access to the oil cooler. (b) Check the oil cooler model number and serial number. Oil cooler model and serial numbers are ink stamped on the side of the cooler with the serial number following the model number. 1. If the oil cooler is either model number 10568B with serial number 101 through 579 or model number 10578B with serial number 101 through 634, or if the model or serial number is illegible, remove and replace it with an oil cooler not of the above model and serial numbers. 2. If the oil cooler is neither model number 10568B with serial number 101 through 579 nor model number 10578B with serial number 101 through 634, make the record entry required in paragraph (c). (c) The inspection and maintenance record entry in paragraph (b)2. may be accomplished by holder of a pilot's certificate issued under Part 61 of the Federal Aviation Regulations on any aircraft owned or operated by him. (d) Any equivalent methods of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. NOTE: A ferry flight to accomplish a needed oil cooler replacement may be issued under the provision of FAR 21.197 by FAA Flight Standards District Offices. Grumman American Service Bulletin Number 156 pertains to this subject. This amendment becomes effective November 10, 1976, to all persons except those to whom it was made effective earlier by airmail letters issued on October 18, 1976.
2005-07-23: The FAA is adopting a new airworthiness directive (AD) for all Dassault Model Falcon 10 series airplanes. This AD requires revising the Limitations section of the airplane flight manual (AFM) to include a statement prohibiting flight into known or forecasted icing conditions, and installing a placard in the flight deck. In lieu of the AFM revision and placard installation, this AD allows identifying the part number of each flexible hose in the wing anti-icing system, performing repetitive detailed inspections of each hose for delamination, and performing corrective actions if necessary. This AD is prompted by a report of delamination of the internal wall of a flexible hose in the wing anti-icing system. We are issuing this AD to prevent collapse of the flexible hoses in the wing anti-icing system, which could lead to insufficient anti-icing capability and, if icing is encountered in this situation, could result in reduced controllability of the airplane.
2001-06-07: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Bombardier Model CL-600-2B19 series airplanes. This action requires a one-time inspection to find chafing or damage of the integrated drive generator cables of the cable harness assembly of the engines, and follow-on actions. This action is necessary to prevent such chafing or damage, which could result in electrical arcing between the cable and an engine cowl door, creating a possible ignition source and consequent fire and/or loss of electrical power on the airplane. This action is intended to address the identified unsafe condition.
2024-04-08: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Canada Limited Partnership Model BD-500-1A10 and BD-500- 1A11 airplanes. This AD was prompted by a report of possible chafing of a power harness at fuselage frame (FR) 65. This AD requires rerouting the power harness, as specified in a Transport Canada AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2024-05-51: The FAA is adopting a new airworthiness directive (AD) for certain General Electric Company (GE) Model CT7-2E1, CT7-2F1, CT7-8A, CT7-8E, CT7-8F5 engines, and various restricted category helicopters with GE Model T700-GE-700,-701A, -701C, -701D/CC, -701D, -401, -401C, CT7-2D or CT7-2D1 engines installed. This AD was prompted by at least four reports of failures of the torque reference tube magnetic insert braze joint of the power turbine drive shaft assembly within the last several months. This AD requires a phase array ultrasonic inspection of the torque reference tube magnetic insert braze joint of the power turbine drive shaft assembly for inadequate braze coverage, and repair or replacement of the power turbine drive shaft assembly if necessary. The FAA previously sent an emergency AD to all known U.S. owners and operators of these engines and helicopters and is now issuing this AD to address the unsafe condition on these products.
2000-25-08: This amendment supersedes an existing airworthiness directive (AD) that applies to Eurocopter France (ECF) Model AS-350B, BA, B1, B2, and D; and AS-355E, F, F1, F2, and N helicopters. That AD currently requires inspecting the main gearbox suspension bi-directional cross beam (cross beam) for cracks, replacing the cross beam if a crack is found, and adding time intervals for repetitive dye-penetrant inspections on cross beams with 5,000 or more hours time-in-service (TIS). This amendment requires the same inspections as the existing AD but would delete repetitive dye-penetrant inspections on cross beams with 5,000 or more hours TIS. This amendment is prompted by the discovery that repetitive dye-penetrant inspections were erroneously required in the existing AD. The actions specified by this AD are intended to prevent failure of the cross beam that could lead to rotation of the main gearbox, severe vibrations, and a subsequent forced landing.
2024-04-05: The FAA is adopting a new airworthiness directive (AD) for all Leonardo S.p.a. Model AB412 and AB412 EP helicopters. This AD was prompted by reports of cracks in the lateral mounts of the main transmission support case. This AD requires repetitive visual inspections and fluorescent penetrant inspections (FPI) and, depending on the results, corrective action, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2010-10-21: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Bombardier Aerospace has completed a system safety review of the CL-600-2C10/CL600-2D15/CL-600-2D24 aircraft fuel system against the new fuel tank safety standards, introduced in Chapter 525 of the Airworthiness Manual through Notice of Proposed Amendment (NPA) 2002-043. The identified non-compliances were assessed using Transport Canada Policy Letter No. 525-001 to determine if mandatory corrective action was required. The assessment showed that certain hydraulic system failure scenarios could lead to a rapid overheat in the hydraulic lines without giving flight crew sufficient time to react before the No. 1 and No. 2 hydraulic system tubing inside the fuel tank reaches the fuel auto ignition temperature. This could result in a fuel tank explosion. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
76-18-10: 76-18-10 MESSERSCHMITT-BOLKOW-BLOHM (MBB): Amendment 39-2719. Applies to Model BO-105A and BO-105C helicopters, Serial Numbers 1 through 280, certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent failure of the engine mount assembly, accomplish the following: (a) For helicopters with 500 hours or less total time in service on the effective date of this AD, comply with paragraph (c) of this AD before the accumulation of 600 hours total time in service. (b) For helicopters with more than 500 hours total time in service on the effective date of this AD, comply with paragraph (c) of this AD within the next 100 hours time in service. (c) Determine the part numbers of the existing right outboard engine mount flanges and washers and their corresponding replacement flanges and washers and replace the existing flanges and washers with the new flanges and washers in accordance with paragraph 2 entitled "Accomplishment Instructions" of MBB BO-105 Service Bulletin No. 60-25, Revision 1, dated October 13, 1975 or an FAA-approved equivalent. This amendment becomes effective on October 1, 1976.
2005-07-25: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Airbus Model A300 B2 and B4 series airplanes; Model A300 B4-600, A300 B4-600R, A300 C4-605R Variant F, and A300 F4-600R (collectively called A300-600) series airplanes; and Model A310 series airplanes. That AD currently requires replacement of the transformer rectifier units (TRUs) in the avionics compartment with new, improved TRUs. This new AD requires replacement of the TRUs installed according to the existing AD with different TRUs that are improved. This AD is prompted by analysis that has revealed that certain diodes installed in the TRUs are the main factor contributing to the continuing TRU failures. We are issuing this AD to prevent failure of the TRUs. Failure of multiple TRUs could result in loss of the thrust reversers, autothrottle, flaps, and various systems (wing/ cockpit window anti-ice, trim tank pumps, and windshield wipers) on the airplane; or display of incorrect information to the flightcrew.
97-09-08: This amendment supersedes Airworthiness Directive AD 82-25-09 which currently requires repetitively inspecting the pilot and co-pilot control wheel sub-assemblies for cracks, and if cracked, modifying the cracked part on the AeroSpace Technologies of Australia, Limited (ASTA), formerly Government Aircraft Factories (GAF) Nomad Models N22S, N22B, and N24A airplanes. This action would retain the repetitive inspection of the pilot and co-pilot control wheel sub-assemblies for cracks, but would include a modification that would terminate the repetitive inspections by replacing or re-working the control wheel sub-assembly with a part of improved design. This superseding action is prompted by cracking in the control wheel sub-assemblies and the manufacture of an improved part that would terminate the repetitive inspection. The actions specified by this AD are intended to prevent failure of the pilot's and co-pilot's control wheels, which, if not detected and corrected, could result in loss of control of the airplane.
2005-07-27: The FAA is superseding an existing airworthiness directive (AD), that is applicable to Aviointeriors S.p.A. (formerly ALVEN), series 312 seats. That AD requires initial and repetitive inspections of the seat central crossmember for cracks, and if necessary, replacing the crossmember with a new crossmember. This ad requires the same actions and adds other crossmember part numbers for inspection. In addition, this AD replaces the original design crossmembers with reinforced design crossmembers as optional terminating actions to the repetitive inspections. This AD results from reports of 88 cracked seat central crossmembers and 60 aisle side crossmembers, to date; and, from the introduction of reinforced optional seat crossmembers by the manufacturer. We are issuing this AD to prevent the loss of the structural integrity of the seat due to cracks in seat crossmembers, which could lead to passenger injury.
2005-07-12: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD requires repetitive detailed and eddy current inspections to detect cracking of the frame web around the cutout for the doorstop intercostal strap at the aft side of the body station 291.5 frame at stringer 16R, and corrective actions if necessary. This AD is prompted by reports of fatigue cracks in the web of the body station 291.5 frame near the forward galley door. We are issuing this AD to detect and correct fatigue cracking of the aft frame and frame support structure of the forward galley door, which could result in a severed fuselage frame web, rapid decompression of the airplane, and possible loss of the forward galley door.
76-07-14: 76-07-14 AERONAUTICA MACCHI: Amendment 39-2578. Applies to Models AL-60 and AL-60B airplanes, certificated in all categories. Compliance is required as indicated. To detect cracks in the engine mounting plates and to prevent possible failure of the engine mount, accomplish the following: (a) Within the next 10 hours time in service after the effective date of this AD, unless already accomplished, and thereafter at intervals not to exceed 50 hours time in service from the last inspection until modified in accordance with paragraph (d) of this AD, comply with the following: (1) Inspect the areas around the periphery of each of the four engine mounting plates for cracks using a dye-penetrant method. (2) Inspect the surfaces inside the concavity of each of the four engine mounting plates, where the lower shock mounts and attaching bolts are inserted, for cracks, using a dye penetrant method, in accordance with Aeronautica Macchi Mandatory Service Bulletin SB-L-0003, dated October 29, 1974, or an FAA-approved equivalent. (b) If a crack is found during an inspection required by paragraph (a) of this AD, before further flight, comply with paragraph (d) of this AD. (c) If no cracks are found during any of the inspections required by paragraph (a) of this AD, within the next 100 hours time in service after the effective date of this AD, or before the accumulation of 1200 hours total airplane time in service, whichever occurs later, comply with paragraph (d) of this AD. (d) Modify each of the four engine mounting plates by adding a reinforcement plate, P/N 6070-47, and replacing the mounting plate shim, P/N 6005, with a new designed shim, P/N 6005A, in accordance with Aeronautica Macchi Mandatory Modification Bulletin, MB-L-0001, Change 1, dated March 5, 1975, or an FAA- approved equivalent. This amendment becomes effective April 26, 1976.
2024-05-05: The FAA is adopting a new airworthiness directive (AD) for all ATR-GIE Avions de Transport R[eacute]gional Model ATR42 and ATR72 airplanes. This AD was prompted by a report of incorrect marking and assembly of the two-way valves for the left- and right-hand engine fire extinguishing systems. This AD requires accomplishing a functional check of an affected part; replacing an affected part if necessary; reporting the functional check results; and prohibiting the installation of affected parts; as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2005-07-20: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737-600, -700, -800, and -900 series airplanes. This AD requires installing and testing an updated version of the operational program software of the flight control computers. This AD is prompted by a report of an airplane pitching up with rapidly decreasing indicated airspeed after the flightcrew set a new altitude into the autopilot. We are issuing this AD to prevent anomalous autopilot operation that produces a hazardous combination of airplane attitude and airspeed, which could result in loss of control of the airplane.
78-12-11: 78-12-11 BRITISH AEROSPACE, INC.: Amendment 39-3237. Applies to (Hawker Siddeley) Model HS-125 Series 700A Airplanes, serial numbers NA 0201 thru NA 0210 and NA 0218, certificated in all categories. Compliance is required as indicated unless already accomplished. To prevent electrical overload and possible fire, accomplish the following in accordance with Section 2, "ACCOMPLISHMENT INSTRUCTIONS" of British Aerospace (formerly Hawker Siddeley Aviation Ltd.) Service Bulletin 24-203 (2653), dated December 14, 1977, or an FAA approved equivalent. (a) Within 10 hours time in service after the effective date of this AD, replace the existing Minyvin 20 beacon light cable and associated marker sleeves and terminal lugs with Minyvin 16 cable and associated B25Y marker sleeves and 36151 terminal lugs or with parts specified in paragraph (b) of this AD. (b) Nyvin 16 or MIL-W-5086 Series 2 cable may be used as alternate replacement cables. Also, FAA approved equivalent marker sleeves including single sleeves with indelible coding may be used in lieu of B25Y sleeves. This amendment becomes effective June 26, 1978.
97-08-07: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-80 series airplanes and Model MD-88 airplanes, that currently requires an inspection to determine the type of fluorescent light ballasts installed in the cabin sidewall; and installation of a protective cover on the ballast, replacement, or removal/disconnection of the ballast, if necessary. That action also requires, for some airplanes, removal of the dust barriers from the outboard ceiling panels, and installation of modified outboard ceiling panels. This amendment would add a requirement to replace certain ballasts on which a protective cover is installed with other ballasts, or removal/disconnection of the ballast. This amendment is prompted by additional reports of heavy smoke and fumes emitting from the ceiling panels in the forward passenger cabin due to the failure of the fluorescent light ballasts. The actions specified in this AD are intended to prevent a fire in the passenger compartment, which could result from failure of the fluorescent light ballast of the upper and lower cabin sidewall, and consequent failure of the dust barriers of the outboard ceiling panel.
2024-03-09: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Canada Limited Partnership Model BD-500-1A11 airplanes. This AD was prompted by a manufacturing issue with an electrical connector that may prevent the connector from self-locking. This AD requires removing the affected connector, installing a new connector, and testing the emergency power supply units (EPSUs), as specified in a Transport Canada AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
76-21-07: 76-21-07 BRITTEN-NORMAN LTD: Amendment 39-2752. Applies to Models BN-2A and BN-2A MK III airplanes, all series, certificated in all categories. Compliance is required within the next 25 hours time in service after the effective date of this AD or before 2 years since new, whichever occurs later, unless already accomplished. To detect corrosion and cracks on the forward face of the engine mounting brackets and prevent possible engine separation, accomplish the following: (a) Inspect the forward face of the engine mounting brackets, P/N NB-20-3463 (BN- 2A) and P/N NB-20-5781 (BN-2A MK III), for corrosion and cracks, in accordance with paragraphs 1 and 2 of the section entitled "Inspection" of Britten-Norman Service Bulletin BN-2/SB,91, issue 1, dated March 23, 1976, or an FAA-approved equivalent. (b) If, during the inspection required by paragraph (a) of this AD, no corrosion is found, re-assemble the engine mounting brackets in accordance with paragraphs 3 and 4of the section entitled "Inspection" of Britten-Norman Service Bulletin BN-2/SB, 91, issue 1, dated March 23, 1976, or an FAA-approved equivalent. (c) If, during the inspection required by paragraph (a) of this AD, minor surface corrosion is found and the bracket surface is free of any pitting, repair and re-assemble the engine mounting brackets in accordance with paragraph 1 of the section entitled "Rectification" of Britten-Norman Ltd. Service Bulletin BN-2/SB.91, issue 1, dated March 23, 1976, or an FAA- equivalent. (d) If, during the inspection required by paragraph (a) of this AD, severe corrosion which is evidenced by surface pitting or a crack is found, replace the engine mounting brackets with new parts of the same part number in accordance with paragraph 2 of the section entitled "Rectification" of Britten-Norman Ltd., Service Bulletin BN-2/SB.91, issue 1, dated March 23, 1976, or an FAA-approved equivalent. This amendment becomes effective November 5, 1976.
2005-07-14: The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A318, A319, A320, and A321 series airplanes. This AD requires an inspection of the spoiler servo control for certain part numbers, and corrective action if necessary. This AD is prompted by a report of a broken piston rod bearing of the spoiler servo control. We are issuing this AD to prevent breakage of the piston rod bearing, which could cause loss of the associated hydraulic system and spoiler extension, and could result in reduced controllability of the airplane.
97-08-08: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 777-200 series airplanes. This action requires repetitive visual inspections of the forward mounts of certain engines to detect damaged, missing, or failed parts, and eventual modification of those engines. Accomplishment of this modification terminates the requirement for repetitive inspections. This amendment is prompted by a report indicating that bolts that attach the yoke of the forward mount to the fan case of the engine have failed due to fatigue cracking. The actions specified in this AD are intended to prevent fatigue cracking in these bolts, which could lead to failure of these bolts and consequent separation of the engine from the wing.
2024-03-06: The FAA is superseding Airworthiness Directive (AD) 2021-20- 13, which applied to certain Bombardier, Inc., Model CL-600-2B16 (604 Variant) airplanes. AD 2021-20-13 required repetitive lubrication and repetitive detailed visual inspections (DVI) and non-destructive test (NDT) inspections of the main landing gear (MLG) shock strut lower pins, and replacement if necessary. This AD continues to require the lubrication and inspections specified in AD 2021-20-13 until the MLG shock strut assembly is modified by replacing the trailing arm bushing and installing new dynamic joint components. This AD was prompted by a new design solution for this potential failure of the shock strut lower pin. The FAA is issuing this AD to address the unsafe condition on these products.
78-01-09 R2: 78-01-09 R2 SHORT BROTHERS LIMITED: Amendment 39-3114 as amended by Amendment 39-3167 is further amended by Amendment 39-3869. Applies to Model SD3-30 airplanes, Serial Numbers SH 3002, SH 3004 through SH 3007, inclusive, and SH 3009 through SH 3011, inclusive, certificated in all categories. To prevent inability to inflate de-icing boots of pneumatic deicing system on the empennage caused by water freezing in system plumbing, accomplish the following: (a) Prior to each flight in which the airplane may be subject to known icing conditions, manually drain the water that collects in the plumbing of the pneumatic deicing system to the empennage in accordance with Section 2 entitled "Accomplishment Instructions" of Short Brothers, Ltd., Alert Service Bulletin SD3-30-A04, Revision 1, dated February 15, 1979, or an FAA-approved equivalent, except that the water need only be drained once each day. In addition, place a placard in full view of the pilot in the cockpit stating: "The deicing system must be drained once each day prior to flight into known icing conditions." NOTE. For the requirements regarding the listing of compliance and method of compliance with this AD in the airplane's permanent maintenance record, see FAR 91.173. (b) Compliance with paragraph (a) of this AD may be terminated upon incorporation of automatic water drainage provisions in accordance with Short Brothers, Ltd., Modification Service Bulletin SD3-30-04 (modification 5332), Revision 2, dated February 15, 1979, or an FAA-approved equivalent. Amendment 39-3114 became effective January 19, 1978. Amendment 39-3167 became effective April 14, 1978. This Amendment 39-3869 becomes effective August 18, 1980.